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ATTITUDE STABILITY OF ARTICULATED GRAVITY-ORIENTED SATELLITES. PART II - LATERAL MOTION
TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES
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By a procedure similar in principle to that for the longitudinal equations of motion, the lateral equations of a specific compound satellite system were derived. The system is substantially identical with that of the previous report Part I. As a result of linearization for small perturbations, the effect of orbit ellipticity vanishes in the lateral motion. Both the general case, i.e. with hinged yaw-stabilizers, are discussed. The latter is considered to be better from the practical standpoint. After calculating numerical examples, the configuration was found to provide damping of the lateral motion to 12 amplitude in about 0.28 orbits, which is a little better than was previously found for the longitudinal models.
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